Aircraft structure vibration condition prediction method under specific working condition

Abstract

The invention relates to a method for predicting the vibration condition of an aircraft structure under a specific working condition, and the method comprises the steps: enabling the time domain information of a vibration response point to be easily and directly measured under the specific working condition on the aircraft structure under a test working condition, and enabling the time domain information of the vibration response point to be not easily and directly measured under the specific working condition; based on the time domain information of the vibration response point which is easy to directly measure on the airplane structure under the specific working condition and the vibration transmissibility matrix under the airplane structure test working condition, calculating the time domain information of the vibration response point which is not easy to directly measure on the airplane structure under the specific working condition, under a test working condition and a specific working condition, vibration response points on an airplane structure are easy to directly measure, and a cross-power spectral density matrix between the vibration response points is not easy to directly measure; in a test working condition, a cross-power spectral density matrix between vibration response points is easy to directly measure on an airplane structure under a specific working condition.

Description

Technical field [0001] The present application belongs to the technical field of the aircraft structural vibration situation, which specifically involves a prediction method of aircraft structure vibration in a particular operating condition. Background technique [0002] According to statistics, there are about one-third of the fault in the airborne equipment failure of the aircraft being caused by the vibration of the aircraft structure, and it is important to determine the vibration of the aircraft structure in each working condition. It is of great significance for the assessment, design, and improvement of airborne equipment. [0003] Under certain conditions, the vibration of the aircraft structure can be directly obtained by the measurement of each vibration response point, but in some specific conditions, the vibration situation of partial vibration response points on the aircraft structure is difficult to perform measurement. For this reason, the current maintenance of t...

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Problems solved by technology

[0006] 3) Empirical formula method, the formula used lacks rigorous derivation, it is difficult to tailor or modify it, and it r

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